Experimental Investigation of Leading Edge Bluntness Effects on Hypersonic Tow-dimensional Inlet

摘要：

　　The leading edge bluntness effects on inlet boundary layer transition had been studied based on a typical hypersonic two-dimensional inlet.Four leading edge radii(R= 0.05mm,R = 0.1mm,R = 0.2mm,R = 0.25mm)had been experimented in FD-07 wind tunnel,including natural transition and artificial transition.The location of boundary layer transition was identified through the corner pressure distribution characteristics and inlet starting,by this method,we had obtained the regular of boundary layer transition location with the leading edge radii.Experimental results showed that,under the wind tunnel condition,the boundary layer transition location moved down stream with increasing the leading edge radius.The inlet would not start for leading edge radius R = 0.25mm and we had designed artificial transition strip based on linear stability theory(LST)to make the inlet start successfully.

关键词： Hypersonic inlet Bluntness effect Boundary layer transition

作者: ZHANG Hong-jun SHEN Qing

作者单位: China Academy of Aerospace Aerodynamics,Beijing 100074,China

会议类型: 国际会议

会议名称: 2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)

会议地点: 上海

会议语种:英文

页码: 1-7

在线出版日期: 2014-09-24（万方平台首次上网日期，不代表论文的发表时间）